Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Rules and Regulations 38011 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 FR 39.19. 

Send information to Attn: Patrick Gillespie, 

Aerospace Engineer, Cabin Safety and 

Environmental Systems Branch, ANM–150S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6429; fax 

(425) 917–6590. Information may be e-mailed 

to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(j) You must use the applicable service 

information contained in Table 2 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Jamco America, Inc., 1018 

80th Street SW., Everett, WA 98203; 

telephone 425–347–4735, ext: 1192 (David 

Crotty); fax 425–353–2343; e-mail 

David_Crotty@jamco-america.com; Internet 

http://jamco-america.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Jamco Service Bulletin 52–2295 ...................................................................................................................... 1 October 10, 2007. 

Jamco Service Bulletin 52–2302 ...................................................................................................................... 1 October 10, 2007. 

Jamco Service Bulletin 52–2303 ...................................................................................................................... 1 October 10, 2007. 

Jamco Service Bulletin 52–2304 ...................................................................................................................... 2 November 1, 2007. 

Jamco Service Bulletin 52–2305 ...................................................................................................................... 1 October 10, 2007. 

Issued in Renton, Washington, on June 18, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–15655 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1227; Directorate 

Identifier 2009–NM–119–AD; Amendment 

39–16347; AD 2010–14–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B16 (CL–604 

Variant) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Two cases of a crack on a ‘‘dry’’ ADG [air 

driven generator] (Hamilton Sundstrand part 

number in the 761339 series), in the aft area 

of the strut and generator housing assembly, 

have been reported on CL–600–2B19 aircraft. 

The same part number is also installed on 

CL–600–2B16 (CL–604) aircraft. Investigation 

determined that the crack was in an area of 

the strut where the wall thickness of the 

casting was below specification, due to a 

manufacturing anomaly in a specific batch of 

ADGs. Structural failure and departure of the 

ADG during deployment could possibly 

result in damage to the aircraft structure. If 

deployment were activated by a dual engine 

shutdown, ADG structural failure would also 

result in loss of hydraulics for the flight 

controls. 

* * * * * 

The unsafe condition is possible loss of 

control of the airplane. We are issuing 

this AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective 

August 5, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 5, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Craig Yates, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7355; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 4, 2010 (75 FR 91). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Two cases of a crack on a ‘‘dry’’ ADG [air 

driven generator] (Hamilton Sundstrand part 

number in the 761339 series), in the aft area 

of the strut and generator housing assembly, 

have been reported on CL–600–2B19 aircraft. 

The same part number is also installed on 

CL–600–2B16 (CL–604) aircraft. Investigation 

determined that the crack was in an area of 

the strut where the wall thickness of the 

casting was below specification, due to a 

manufacturing anomaly in a specific batch of 

ADGs. Structural failure and departure of the 

ADG during deployment could possibly 

result in damage to the aircraft structure. If 

deployment were activated by a dual engine 

shutdown, ADG structural failure would also 

result in loss of hydraulics for the flight 

controls. 

This directive gives instructions to check 

the part number of the installed ADG and, for 

ADGs with a part number in the 761339 

series, the serial numbers of the ADG and the 

strut and generator housing assembly are also 

to be checked. If these serial numbers are 

within specified ranges * * *, initial and 

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38012 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Rules and Regulations 

subsequent repeat fluorescent penetrant 

inspections of the ADG strut are required. 

This directive also gives instructions to 

perform a fluorescent penetrant inspection 

after each unscheduled in-flight ADG 

deployment and a [general] visual inspection 

after each unscheduled on-ground ADG 

deployment. Instructions regarding reidentification (where applicable) and 

replacement parts are also included. 

The unsafe condition is possible loss of 

control of the airplane. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request to Change Table 1 

Bombardier Aerospace (Bombardier) 

asks that we change Table 1 of the 

NPRM to refer to Bombardier Alert 

Service Bulletin A604–24–017, Revision 

01, dated January 15, 2007, instead of 

Bombardier Alert Service Bulletin 

A604–24–017, dated May 6, 2005. 

Bombardier states that Revision 01 is 

referenced throughout the NPRM. 

We do not agree with the commenter. 

The service information identified in 

Table 1 of this AD is to give credit for 

inspections done before the effective 

date of the AD in accordance with 

previously issued service information. 

Revision 01 of Bombardier Alert Service 

Bulletin A604–24–017 is the 

appropriate source of service 

information for accomplishing the 

actions required after the effective date 

of this AD. We have made no change to 

the AD in this regard. 

Request to Change Paragraph (f)(4) 

Bombardier asks that the inspection 

type specified in paragraph (f)(4) of the 

NPRM be changed from a general visual 

inspection to a fluorescent penetrant 

inspection. Bombardier states that 

Bombardier Alert Service Bulletin 

A604–24–017, Revision 01, dated 

January 15, 2007, specifies a fluorescent 

penetrant inspection. 

We agree with the commenter. Part III 

of the Transport Canada Civil Aviation 

(TCCA) AD, which equates to paragraph 

(f)(4) of this AD, requires merely 

‘‘inspecting’’ the ADG strut; therefore, to 

further clarify the type of inspection, we 

inadvertently described a general visual 

inspection. However, Bombardier Alert 

Service Bulletin A604–24–017, Revision 

01, dated January 15, 2007, specifies a 

fluorescent penetrant inspection of the 

ADG strut for cracks, which we 

subsequently determined is the correct 

inspection type. Therefore, we have 

changed paragraph (f)(4) of this AD to 

require a fluorescent penetrant 

inspection of the ADG strut for cracks. 

Explanation of Additional Changes 

Made to This AD 

We have changed this AD to identify 

the name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Paragraph (f)(1)(ii)(C)(1) of this AD 

was changed to clarify that the subparagraphs identified within that 

paragraph as (f)(6), (f)(7), and (f)(8), 

should have been identified as 

paragraphs (f)(5), (f)(6), and (f)(7). 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified hourly 

labor rate. 

Costs of Compliance 

We estimate that this AD will affect 

378 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $64,260, or 

$170 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

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Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Rules and Regulations 38013 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–14–02 Bombardier, Inc.: Amendment 

39–16347. Docket No. FAA–2009–1227; 

Directorate Identifier 2009–NM–119–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 5, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes; certificated in any category; serial 

numbers 5408 through 5665 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Two cases of a crack on a ‘‘dry’’ ADG [air 

driven generator] (Hamilton Sundstrand part 

number in the 761339 series), in the aft area 

of the strut and generator housing assembly, 

have been reported on CL–600–2B19 aircraft. 

The same part number is also installed on 

CL–600–2B16 (CL–604) aircraft. Investigation 

determined that the crack was in an area of 

the strut where the wall thickness of the 

casting was below specification, due to a 

manufacturing anomaly in a specific batch of 

ADGs. Structural failure and departure of the 

ADG during deployment could possibly 

result in damage to the aircraft structure. If 

deployment were activated by a dual engine 

shutdown, ADG structural failure would also 

result in loss of hydraulics for the flight 

controls. 

This directive gives instructions to check 

the part number of the installed ADG and, for 

ADGs with a part number in the 761339 

series, the serial numbers of the ADG and the 

strut and generator housing assembly are also 

to be checked. If these serial numbers are 

within specified ranges * * *, initial and 

subsequent repeat fluorescent penetrant 

inspections of the ADG strut are required. 

This directive also gives instructions to 

perform a fluorescent penetrant inspection 

after each unscheduled in-flight ADG 

deployment and a [general] visual inspection 

after each unscheduled on-ground ADG 

deployment. Instructions regarding reidentification (where applicable) and 

replacement parts are also included. 

The unsafe condition is possible loss of 

control of the airplane. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 400 flight hours after the 

effective date of this AD, inspect to 

determine the part number of the installed 

ADG and accomplish the actions required by 

paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as 

applicable. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the ADG can 

be conclusively determined from that review. 

(i) If the part number of the ADG is 604– 

90800–23 (Hamilton Sundstrand part number 

1711405), the strut wall thickness is within 

specification and no further action is 

required by this paragraph. 

(ii) If the part number of the ADG is 604– 

90800–1, –17 or –19 (Hamilton Sundstrand 

part number in the 761339 series), inspect to 

determine the ADG serial number and do the 

applicable action required by paragraph 

(f)(1)(ii)(A), (f)(1)(ii)(B), or (f)(1)(ii)(C) of this 

AD. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the serial number of the ADG 

can be conclusively determined from that 

review. 

(A) If the serial number of the ADG is 2000 

or higher, the strut wall thickness is within 

specification and only re-identification is 

required. Do the actions required by 

paragraph (f)(8) of this AD. 

(B) If the serial number of the ADG is in 

the range 0101 through 1999 inclusive, and 

the symbol 24–3 is marked in the serial 

number block of the identification plate, the 

strut wall thickness is within specification 

and only re-identification is required. Do the 

actions required by paragraph (f)(8) of this 

AD. 

(C) If the serial number of the ADG is in 

the range 0101 through 1999 inclusive, and 

the symbol 24–3 is not marked in the serial 

number block of the identification plate, 

inspect to determine the serial number of the 

strut and generator housing assembly and do 

the applicable action required by paragraph 

(f)(1)(ii)(C)(1) or (f)(1)(ii)(C)(2) of this AD, as 

applicable. 

Note 1: Guidance on serial number location 

can be found in Figure 1, Sheet 1, of 

Hamilton Sundstrand Service Bulletin 

ERPS10AG–24–3, Revision 3, dated March 

12, 2009. 

(1) If the serial number of the strut and 

generator housing assembly is in the range 

0001 through 2503 inclusive, the fluorescent 

penetrant inspection specified in paragraph 

(f)(2) of this AD is required. For airplanes on 

which an unscheduled in-flight or on-ground 

ADG deployment has occurred after 

accomplishing the actions required by this 

paragraph, do the actions required by 

paragraph (f)(5), (f)(6), or (f)(7) of this AD, as 

applicable. 

(2) If the serial number of the strut and 

generator housing assembly is 2504 or higher, 

the strut wall thickness is within 

specification and only re-identification is 

required. Do the actions required by 

paragraph (f)(8) of this AD. 

(2) For airplanes having a strut and 

generator housing assembly identified in 

paragraph (f)(1)(ii)(C)(1) of this AD, except 

for airplanes with serial numbers 5611 

through 5665 on which Bombardier 

conducted the initial fluorescent penetrant 

inspection prior to aircraft delivery and on 

which the ADG has not been replaced since 

aircraft delivery: Within 400 flight hours after 

the effective date of this AD, do a fluorescent 

penetrant inspection of the ADG strut, and 

replace the ADG, as applicable, in 

accordance with paragraphs 2.A., 2.C., and 

2.D. of the Accomplishment Instructions in 

Bombardier Alert Service Bulletin A604–24– 

017, Revision 01, dated January 15, 2007. If 

the ADG is replaced by an ADG with part 

number 604–90800–23 (Hamilton 

Sundstrand part number 1711405), no further 

action is required by this paragraph. 

Accomplishing the requirements in 

paragraph (f)(4) of this AD is required for 

airplanes on which each ADG has been 

inspected in accordance with this paragraph. 

(3) Accomplishment of the fluorescent 

penetrant inspection before the effective date 

of this AD in accordance with the applicable 

service information identified in Table 1 of 

this AD is acceptable for compliance with the 

requirements of paragraph (f)(2) of this AD. 

TABLE 1—ACCEPTABLE SERVICE INFORMATION

Document Revision Date 

Bombardier Alert Service Bulletin A604-24-017 ............................................................................ Original ........................ May 6, 2005. 

Hamilton Sundstrand Service Bulletin ERPS10AG–24–3 ............................................................. Original ........................ April 14, 2005. 

Hamilton Sundstrand Service Bulletin ERPS10AG–24–3 ............................................................. Revision 1 ................... April 19, 2005. 

Hamilton Sundstrand Service Bulletin ERPS10AG–24–3 ............................................................. Revision 2 ................... November 14, 2006. 

Hamilton Sundstrand Service Bulletin ERPS10AG–24–3 ............................................................. Revision 3 ................... March 12, 2009. 

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Note 2: In Hamilton Sundstrand Service 

Bulletin ERPS10AG–24–3, the fluorescent 

penetrant inspection is referred to as a 

‘‘penetrant check.’’ 

(4) As of the effective date of this AD, for 

airplanes on which the inspection required 

by paragraph (f)(2) of this AD has been done 

and on which a scheduled ADG operational 

test is performed: Before further flight after 

each test, do a fluorescent penetrant 

inspection of the ADG strut for cracks, and 

replace the ADG if any crack is found, in 

accordance with paragraphs 2.A., 2.C., and 

2.D. of the Accomplishment Instructions in 

Bombardier Alert Service Bulletin A604–24– 

017, Revision 01, dated January 15, 2007. If 

the ADG is replaced by an ADG with part 

number 604–90800–23 (Hamilton 

Sundstrand part number 1711405), no further 

action is required by this paragraph. 

(5) As of the effective date of this AD, for 

airplanes identified in paragraph 

(f)(1)(ii)(C)(1) of this AD on which an 

unscheduled in-flight ADG deployment 

occurs: Before further flight after each 

deployment, do a general visual inspection of 

the ADG strut for cracks, and replace the 

ADG if any crack is found, in accordance 

with paragraphs 2.A., 2.B., and 2.D. of the 

Accomplishment Instructions in Bombardier 

Alert Service Bulletin A604–24–017, 

Revision 01, dated January 15, 2007. [If the 

ADG is replaced by an ADG with part 

number 604–90800–23 (Hamilton 

Sundstrand part number 1711405), no further 

action is required by this paragraph.] The 

general visual inspection required by this 

paragraph is not required if the fluorescent 

penetrant inspection required by paragraph 

(f)(6) of this AD is performed before further 

flight. 

(6) For airplanes identified in paragraph 

(f)(1)(ii)(C)(1) of this AD on which an 

unscheduled in-flight ADG deployment 

occurs: Within 3 days or 10 hours time-inservice, whichever comes first, after each 

deployment, perform a fluorescent penetrant 

inspection of the ADG strut, and replace the 

ADG, as applicable, in accordance with 

paragraphs 2.A., 2.C., and 2.D. of the 

Accomplishment Instructions in Bombardier 

Alert Service Bulletin A604–24–017, 

Revision 01, dated January 15, 2007. If the 

ADG is replaced by an ADG with part 

number 604–90800–23 (Hamilton 

Sundstrand part number 1711405), no further 

action is required by this paragraph. 

(7) For airplanes identified in paragraph 

(f)(1)(ii)(C)(1) of this AD on which an 

unscheduled on-ground ADG deployment 

task is done: Before further flight after each 

deployment, do a general visual inspection of 

the ADG strut for cracks, and replace the 

ADG if any crack is found, in accordance 

with paragraphs 2.A., 2.B., and 2.D. of the 

Accomplishment Instructions in Bombardier 

Alert Service Bulletin A604–24–017, 

Revision 01, dated January 15, 2007. If the 

ADG is replaced by an ADG with part 

number 604–90800–23 (Hamilton 

Sundstrand part number 1711405), no further 

action is required by this paragraph. 

(8) For airplanes identified in paragraphs 

(f)(1)(ii)(A), (f)(1)(ii)(B), and (f)(1)(ii)(C)(2) of 

this AD: Within 400 flight hours after the 

effective date of this AD, re-identify the ADG, 

in accordance with the Accomplishment 

Instructions in Bombardier Service Bulletin 

604–24–019, dated October 1, 2007. 

Following re-identification, no further action 

is required by this paragraph. 

Note 3: Paragraph (f)(8) of this AD is 

applicable only if required by paragraph 

(f)(1)(ii)(A), (f)(1)(ii)(B), or (f)(1)(ii)(C)(2) of 

this AD. The strut wall thickness of the ADGs 

specified in these paragraphs is not below 

specification. 

(9) As of the effective date of this AD, no 

person may install an ADG having part 

number 604–90800–1, –17, or –19 (Hamilton 

Sundstrand part number in the 761339 

series) on any airplane if the serial number 

of the ADG is in the range 0101 through 1999 

strut and the serial number of the generator 

housing assembly is in the range 0001 

through 2503. 

Note 4: The Bombardier CL–604 Illustrated 

Parts Catalog specifies that, for an ADG with 

a Hamilton Sundstrand part number in the 

761339 series, future procurement is to be an 

ADG with Hamilton Sundstrand part number 

1711405. 

(10) Although Bombardier Alert Service 

Bulletin A604–24–017, Revision 01, dated 

January 15, 2007; and Service Bulletin 604– 

24–019, dated October 1, 2007; specify 

submitting certain information to the 

manufacturer, this AD does not require that 

submission. 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or service information 

tells you to submit information to the 

manufacturer, paragraph (f)(10) of this AD 

specifies that such submittal is not required. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Program Manager, Continued Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7300; fax (516) 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(h) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–24, dated May 19, 2009; 

Bombardier Alert Service Bulletin A604–24– 

017, Revision 01, dated January 15, 2007; and 

Bombardier Service Bulletin 604–24–019, 

dated October 1, 2007; for related 

information. 

Material Incorporated by Reference 

(i) You must use Bombardier Alert Service 

Bulletin A604–24–017, Revision 01, dated 

January 15, 2007; and Bombardier Service 

Bulletin 604–24–019, dated October 1, 2007; 

as applicable; to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 

514–855–7401; e-mail 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on June 17, 

2010. 

Robert D. Breneman, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–15818 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1224; Directorate 

Identifier 2009–NM–118–AD; Amendment 

39–16351; AD 2010–14–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–200, –300, –400, 

and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Model 737– 

300, –400, and –500 series airplanes. 

That AD currently requires an 

WReier-Aviles on DSKGBLS3C1PROD with RULES